Technology gaps exist for design and certification of bonded repair of large composite structures under multiaxial loading. They are 1) consideration of delamination failure without including the matrix cracking-induced stress concentration at a ply interface; 2) use of test data from a simple geometry for the failure prediction of a complex repaired configuration with a multiaxial stress state and spatial variation of the local stress ratio; 3) pre-assumed failure modes without including the multiaxial stress state-driven damage initiation and progression; and 4) lack of a rational modeling approach for the damage evaluation of a full-scale structure to balance the computational efficiency and solution accuracy. Our primary goal of this study is to extend our modeling capability for a bonded composite structure subjected to multiaxial loading and to demonstrate a global-local modeling capability for the high-fidelity damage evaluation at a critical location of a full-scale composite wing section. Multiaxial tests for a scarf repaired component are performed via the bi-axial cruciform apparatus while a capability demonstration is conducted using the strain survey test of a full-scale wing section via the developed test rig. After verification of the global response prediction, the developed global-local modeling strategy is used to evaluate the damage progression at a critical location with a detected initial defect.